A method for determining the transfer orbit of a lunar probe

Abstract

The invention provides a method for determining the transfer orbit of the lunar probe, which is based on the establishment of a force model at the time of separation between the lunar probe and the ket, combined with the high-precision global satellite navigation and positioning data before and after the separation of the ket, and solving the pre-separation and the orbital parameters of the ket after separation; then, using the law of conservation of momentum, the separation force between the lunar probe and the ket at the time of separation, and the instantaneous space attitude of the ket (the direction of the separation force) are solved; finally, the calculation of the orbital transfer orbit of the lunar probe at the launch stage is obtained result. The invention can obtain a relatively high-precision lunar probe into the transfer orbit, and provide a relatively high-precision initial orbit for the subsequent midway correction of the lunar probe.

Description

technical field [0001] The invention belongs to the field of spacecraft dynamics research, and in particular relates to a method for determining the launch orbit of a lunar probe. Background technique [0002] The launch of the lunar probe into the transfer orbit is the first space orbit for the probe to transfer to the moon and rendezvous with it after the probe is separated from the final stage of the launch vehicle. The starting point is usually represented by orbital epochs, position and velocity in the inertial coordinate system, or by orbital epochs and Kepler orbital elements. The Lunar Probe Measurement and Control Center can obtain the space trajectory of the Lunar Probe flying to the Moon over time based on the determination results of the injection transfer orbit. [0003] For the determination of the traditional lunar probe's launch and transfer orbit, the measurement data comes from the ground radar tracking and measurement system, relying on the ground radar s...

AI Technical Summary

Problems solved by technology

[0004] The GNSS receiver carried by my country's Chang'e series of lunar probes is turned off during the launch phase. Its main design purpose is to track and measure the probes returning to the earth. Therefore, the lunar probes separated from the final stage of the launch vehicle are launched into the transfer orbit It is determined that the support of GNSS data cannot be obtained; in addition, when the lunar probe is separated from the last stage of the launch vehicle, it is affected by the spring separation force, which leads to the failure of the lunar probe to achieve high orbit determination accuracy when it is launched into the transfer orbit

[0005] In summary, the existing lunar probes based on traditional ground radar system tracking and measurement have low accuracy in determining the transfer orbit; in addition, since the separation force of the space spring cannot be measured on the spot, the force model for determining the orbit of the probe is not accurate enough. whole

Therefore, for a long time, the launch of the lunar probe into the transfer orbit has definitely not been able to achieve high-precision technical status. For the orbit correction of the probe on the way to the moon, it has always been a technical bottleneck to be solved.

Images